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Near-Earth Object Flyby Second Generation Microspacecraft

Here is an example concept for a Near-Earth-Object Flyby Second-Generation Microspacecraft (SGM). The spacecraft autonomously provides imaging and imaging spectroscopy of a near-Earth asteroid or comet for spacecraft solar ranges of 0.8 to 1.2 Astronomical Units (AU) and Earth ranges up to 1.6 AU. Estimated spacecraft wet mass, launch configuration size, and load power are, respectively, 5.5 kg, 20 cm x 33 cm x 27 cm, and 5 to 13 W - depending whether the transmitter is off or on.

Developed in 1993-1995, a vision, approach, and example system concepts for Second-Generation Microspacecraft (SGM) have the intent of helping enable NASA's paradigm shift to less expensive, more frequent missions. Envisioned is a future in which a significant number of missions can be carried out with SGM that have low life-cycle cost, provide a high return on investment, allow for frequent flights and contribute to innovation in technology.

Key elements to realizing this vision include reducing spacecraft resource requirements and complexity, minimizing spacecraft size and mass, using core building blocks and extensive spacecraft autonomy, and eliminating non-cost-effective redundancy. It is important to target appropriate, focused missions and payloads, using on-board analysis and data compression, minimizing spacecraft power needs, and using low-nuclear or, preferably, non-nuclear energy sources. SGM system concepts that are consistent with this approach include the Outer Solar System Flyby SGM, Near-Earth-Object Flyby SGM, Near- Earth-Object Rendezvous SGM, and Space Physics Fields and Particles SGM.